US4438793A - Aerial refueling boom nozzle - Google Patents
Aerial refueling boom nozzle Download PDFInfo
- Publication number
- US4438793A US4438793A US06/259,838 US25983881A US4438793A US 4438793 A US4438793 A US 4438793A US 25983881 A US25983881 A US 25983881A US 4438793 A US4438793 A US 4438793A
- Authority
- US
- United States
- Prior art keywords
- housing
- nozzle
- boom
- fitting
- section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 239000004020 conductor Substances 0.000 claims description 4
- 239000012530 fluid Substances 0.000 claims description 2
- 239000004033 plastic Substances 0.000 claims description 2
- 230000000007 visual effect Effects 0.000 claims 2
- 238000000034 method Methods 0.000 description 7
- 238000012986 modification Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 230000001066 destructive effect Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D39/00—Refuelling during flight
- B64D39/06—Connecting hose to aircraft; Disconnecting hose therefrom
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S285/00—Pipe joints or couplings
- Y10S285/92—Remotely controlled
Definitions
- the present invention relates generally to a nozzle and, more particularly, to a nozzle for an aerial refueling boom.
- an aerial refueling tanker incorporates a boom which extends outwardly and downwardly from the rear of the tanker.
- the boom is controlled by an operator in the tanker who can guide a nozzle on the end of the boom into engagement with a receptacle in the receiver aircraft.
- latches within the receptacle are shifted by hydraulic actuators to lock the nozzle into the receptacle.
- actuators are operated automatically or by personnel in the receiver aircraft.
- the receiver latch release mechanism is triggered by the boom operator in the tanker aircraft by means of an electrical signal transmitted through communications coils at the nozzle/receptacle interface.
- the third method is called "Brute Force" which requires decreasilng the speed of the receiver aircraft sufficiently relative to the refueling tanker either by reducing its power or by extending flaps or other drag inducing devices to put sufficient force on the nozzle and, in turn, on the latches of the receptacle to overpower the hydraulic pressure which controls the latches.
- the first two methods have proved to be not sufficiently reliable and the third method is somewhat dangerous and can cause aircraft damage.
- One method which has been proposed for achieving this result involves the use of a pneumatic actuating cylinder and a pressurized gas storage bottle for operating the latches in the boom nozzle.
- the requirement in such an arrangement for a pressurized gas storage bottle necessitates that the bottle be recharged before every mission of the refueling tanker.
- use of a gas storage bottle requires major modifications to be made to the boom in order to accept the bottle. Such modifications would add considerable expense to the cost of the refueling system.
- recharging of the gas storage bottle involves considerable maintenance service throughout the lifetime of the aircraft.
- high pressure gas may not always be available for recharging the bottles at certain airfields where the refueling tanker may be required to land.
- a nozzle for an aerial refueling boom comprising a housing containing a solenoid including a coil and an armature movable parallel to the longitudinal axis of the housing between first and second positions.
- a pair of latches are mounted in recesses on opposite sides of the housing each pivotable about an axis transverse to the longitudinal axis of the housing.
- Spring means normally bias the latches inwardly into the recesses into a release or unlock position.
- Radially movable cam elements in the housing engage the undersides of the latches. Means are provided operatively connecting the cam elements and the armature.
- the cam elements In the first position of the armature the cam elements are located in a retracted position allowing the latches to assume their release position. In the second position of the armature the cam elements are forced outwardly via the connecting means to an extended position pushing the latches outwardly from the recesses into a locking position.
- the boom operator may control the solenoid and, thus, operate the nozzle latches, thereby rapidly disconnecting such latches from the receptacle latches in the receiver aircraft.
- FIG. 1 is the vertical longitudinal sectional view through the nozzle of the present invention showing the nozzle latches in their locking position;
- FIG. 2 is the longitudinal sectional view taken along line 2--2 of FIG. 1;
- FIG. 3 is a transverse sectional view taken along line 3--3 of FIG. 1;
- FIG. 4 is a rear end view of the nozzle illustrated in FIGS. 1 and 2;
- FIG. 5 is a fragmentary transverse sectional view taken along line 5--5 of FIG. 1 showing the pivot pin for one of the latches;
- FIG. 6 is a longitudinal sectional view showing the rear portion of the nozzle with the latches thereof in their retracted, unlocked position.
- the boom nozzle of the present invention comprises a housing 12 having a forward inlet section 14 and a rear outlet section 16.
- the forward section of the housing is adapted to be connected to the boom of an aerial refueling tanker while the outlet section of the nozzle is adapted to couple with a receptacle in the receiver aircraft, not shown.
- a ball joint, generally designated 18, is provided between the inlet and outlet sections of the housing.
- the ball joint is formed by a rear partially hemispherical male portion 20 of the inlet section 14 of the housing which has a rotatable, sliding fit within a partially hemispherical forward female portion 22 of the outlet section 16 of the housing.
- a spring loaded universal joint stem assembly, generally designated 24, is centrally supported in the inlet section 14 of the housing by a radially extending strut 26.
- the stem assembly 24 is closed at its forward end by a protective cover 27.
- the outlet section 16 of the housing embodies an inner part 28 which is coupled to the stem assembly 24 by a universal joint, generally designated 30.
- the inner part 28 is supported in the outlet section of the housing by radial webs 31, as best seen in FIG. 3.
- the rear of the outlet section 16 of the housing contains a poppet 32 which is biased rearwarded by a spring 34 to normally engage a sealing ring 36 on the interior of the housing prior to engaging the nozzle with the receptacle in the receiver aircraft, as shown in FIG. 6.
- Such poppet shifts forwardly in the housing to the position illustrated in FIG. 1 when the nozzle is engaged with the receptacle so that fluid may flow through the nozzle into the receiver aircraft fuel tank.
- a pair of recesses 38 are formed in the opposite sides of the outlet section 16 of the housing. Each recess receives a latch 40 which is pivotably mounted on a pin 42 which extends transversely of the longitudinal axis of the nozzle. Rods 44 biased by springs 46 normally urge the latches 40 inwardly into the recesses in their unlocked position as seen in FIG. 6. When the latches are actuated outwardly, they engage with mating latch elements 48 of the receiver aircraft receptacle, not shown, which receives the boom nozzle.
- a solenoid For controlling the position of the latches 40, there is provided a solenoid, generally designated 50, which is mounted within a cavity 52 in the forward portion of the inner part 28 of the outlet section of the housing.
- the solenoid includes a coil 53 which surrounds an armature 54 which is slidable along the longitudinal axis of the nozzle.
- Two springs 56 and 57 normally bias the armature to an extended position as shown in FIG. 1.
- Radially movable cam elements 58 are mounted in bores 60 in the wall of the outlet section of the housing so that the outer curved surfaces 62 of the cam elements engage the undersides 64 of the latches.
- a plunger 66 is slidably mounted in the rear of the armature 54.
- Toggle links 68 are pivotably mounted by pins 70 and 72 to the cam elements 58 and plunger 66, respectively.
- the solenoid 50 as shown in FIG. 1 is in its de-energized condition allowing the springs 56 and 57 to push the armature 54 and, hence, the plunger in the rightward direction.
- This causes the links 68 to push the cam elements 58 outwardly in their respective bores 60, thereby pushing the latches 40 outwardly in the recesses 38 where they will latch to and lock with the receptacle latches 48.
- the links provide an unyielding stiff member between the latches to prevent their depression.
- the conductors 74 for the coil of the solenoid extend through a central bore 76 in the shaft 78 of the stem assembly 24 and outwardly through a passage 80 in the strut 26 to a terminal box 82 on the exterior of the nozzle housing.
- the conductors 74 are connected to terminals 84, only one being seen in FIG. 1, which in turn are coupled to conductors 86 leading to the boom operator controls in the aerial refueling tanker.
- the boom operator may directly control the latches 40 and, thereby, effect a disconnection between the boom nozzle and the receiver aircraft in an emergency situation.
- the solenoid utilized in the nozzle of the present invention is very compact and, therefore, may be easily installed in a nozzle of the same size as conventional nozzles, and without the requirement of modifying the boom for the nozzle. Furthermore, the solenoid operates off of power which is already available in the refueling tanker, thus not requiring substantial modification of the boom and the installation therein of pressurized gas storage bottles as has been proposed in the past.
- the solenoid coil is energized by the boom operator thereby causing the armature 54 to shift in a leftward direction to the position illustrated in FIG. 6.
- This allows the spring biased rods 44 to push the latches 40 inwardly into the recesses 38 so that the links 68 and plunger 66 will assume the position seen in FIG. 6.
- the boom nozzle may disconnect from the receiver aircraft receptacle, whereupon the spring 34 will push the poppet 32 to its closed position as illustrated in FIG. 6 thus closing the end of the nozzle and preventing any fuel from escaping from the end of the boom.
- An inlet fitting 90 is mounted in the forward end of the inlet section 14 of the housing.
- the fitting is externally threaded as indicated at 92 for coupling with the end of the boom, not shown.
- a generally annular non-destructive structural "fuse" arrangement is provided between the fitting 90 and the inlet section of the housing.
- Such arrangement comprises a plurality of structural fuses or detent elements 96 spaced circumferentially around the end of the housing. For example, there may be from twelve to sixteen of such fuses depending on the diameter of the nozzle.
- Each detent element 96 embodies an inner semi-hemispherical cam surface 98 which is normally engaged with a dished detent recess 100 in the outer surface of the fitting 90.
- the detent element 96 is urged into the recess 100 by a spring 102 surrounding at its outer end a spring guiding element 104.
- the detent assemblies are retained in the inlet section 14 of the housing by a clamping ring 106.
- O-rings 108 are arranged on opposite sides of the detent assembly between the outer surface 110 of the forward end of the inlet section 14 and the clamping ring 106, while a second set of O-rings 112 are positioned on opposite sides of the detent arrangment between the inner surface of the housing and the outer surface of the fitting 90.
- the detent arrangement is provided to prevent bending loads sufficiently harmful to permanently damage the aerial refueling boom.
- the number of detent elements 96 and the force of the springs 102 are chosen such that when bending forces become excessive, the force acting upon the detent elements will overcome their corresponding springs so that the elements will be cammed out of their respective detent recesses sufficiently far that they no longer retain the fitting 90 attached to the nozzle housing.
- the nozzle housing will disconnect from the fitting 90.
- the major portion of the nozzle will remain attached to the receptacle in the receiver aircraft while the fitting 90 will remain attached to the end of the boom on the aerial refueling aircraft. Since the detent assemblies are non-destructive, they need not be replaced when reassembling the nozzle housing to the fitting when the two aircraft return to ground for maintenance.
- Shear screws 114 shown in FIG. 2 are provided in the universal joint 30 for preventing excessive tension loads being applied to the boom.
- the yoke 116 extending forwardly from the inner part 28 of the outlet section 16 of the housing includes a support ring 118 which is attached to the yoke by the shear screws 114.
- the pivot pins 120 of the U-joint which are connected to the center ring 122 are mounted in the support ring 118.
- a second set of pins 124 pivotally connect the inner ring 122 of the U-joint to the stem shaft 78, as seen in FIG. 2.
- a rearwardly facing annular stop shoulder 126 is provided on the inlet section 14 of the nozzle housing spaced in front of the forward edge 128 of the female portion 22 of the ball joint 18.
- a deformable ring 130 is mounted on the forward edge 128 of the outlet section of the housing.
- Such ring may be formed of a suitable plastic which is capable of being permanently deformed, such as polytetrafluoroethylene (Teflon).
- the ring 130 will contact the shoulder 126 on the inlet housing deforming the ring thereby indicating operation of the nozzle out of normal yet not sufficient to activate the internal mechanical fuse arrangement 94 or separate the shear screws 114.
- any mechanical fuse whether it be a shear or tensile separating type, can be partially separated from short duration impacts and become weakened so that normal operating stresses will finally cause separation. It is, therefore, highly desirable to have a reliable indication prior to such separation that the maximum allowable deflection angle has been exceeded, which indication is achieved by the deformable ring 128 of the present invention.
- the present invention provides a compact and inexpensive latch actuating mechanism which may be installed in a boom nozzle without any modification of the boom or enlargement of the nozzle, and which is effective to provide a suitable locking engagement with the latches on the receptacle of a receiver aircraft, and may be actuated by the boom operator in the refueling tanker.
- the present invention provides non-destructive structural "fuses" in the form of the detent arrangement 94 and shear screws 114 to avoid damage to the boom resulting from excessive angular deflections or tension loads occurring as the result of the tanker and receiver aircraft moving outside of their normal safe operating range relative to each other.
- the ring 130 if deformed, provides an indication to the maintenance personnel that the structural fuses 94 and 114 should be inspected.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
Description
Claims (10)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US06/259,838 US4438793A (en) | 1981-05-04 | 1981-05-04 | Aerial refueling boom nozzle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US06/259,838 US4438793A (en) | 1981-05-04 | 1981-05-04 | Aerial refueling boom nozzle |
Publications (1)
Publication Number | Publication Date |
---|---|
US4438793A true US4438793A (en) | 1984-03-27 |
Family
ID=22986623
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US06/259,838 Expired - Lifetime US4438793A (en) | 1981-05-04 | 1981-05-04 | Aerial refueling boom nozzle |
Country Status (1)
Country | Link |
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US (1) | US4438793A (en) |
Cited By (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4535826A (en) * | 1983-08-29 | 1985-08-20 | Bell Edward D | Apparatus for rapid refueling of armored fighting vehicles |
US5004023A (en) * | 1990-03-30 | 1991-04-02 | Monticup Jr Anthony | Gasoline nozzle with emergency shut-off |
US5988332A (en) * | 1997-07-23 | 1999-11-23 | Marzocchi S.P.A. | Hydraulic shock absorber |
US20060011782A1 (en) * | 2004-07-14 | 2006-01-19 | The Boeing Company | In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components |
US20060102791A1 (en) * | 2004-11-18 | 2006-05-18 | The Boeing Company | Interoperable aerial refueling apparatus and methods |
US20060192053A1 (en) * | 2005-02-25 | 2006-08-31 | Crangle Gage B | Systems and methods for controlling flexible communication links used for aircraft refueling |
US20060278763A1 (en) * | 2005-06-09 | 2006-12-14 | The Boeing Company | Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods |
US20060278759A1 (en) * | 2005-06-09 | 2006-12-14 | The Boeing Company | System and methods for distributing loads from fluid conduits, including aircraft fuel conduits |
US20060278760A1 (en) * | 2005-06-09 | 2006-12-14 | The Boeing Company | Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems |
US20060284019A1 (en) * | 2005-06-20 | 2006-12-21 | Takacs John F | Controllable refueling drogues and associated systems and methods |
US20070069071A1 (en) * | 2005-06-08 | 2007-03-29 | The Boeing Company | Systems and methods for providing back-up hydraulic power for aircraft, including tanker aircraft |
US20070102583A1 (en) * | 2005-10-26 | 2007-05-10 | Cutler Theron L | Systems and methods for reducing surge loads in hose assemblies, including aircraft refueling hose assemblies |
US20070215753A1 (en) * | 2005-09-01 | 2007-09-20 | Schuster John H | Systems and methods for controlling an aerial refueling device |
WO2008045116A2 (en) * | 2005-12-22 | 2008-04-17 | Ge Aviation Systems Llc | Controllable drogue |
EP1916186A1 (en) * | 2006-10-24 | 2008-04-30 | Eads Construcciones Aeronauticas S.A. | Refueling boom with a fail-safe roll-pitch device |
US20080302916A1 (en) * | 2005-03-24 | 2008-12-11 | Speer Thomas E | Systems and methods for automatically and semiautomatically controlling aircraft refueling |
EP2343240A2 (en) | 2010-01-08 | 2011-07-13 | EADS Construcciones Aeronauticas, S.A. | System for disconnecting a fuel transfer boom. |
WO2013043290A1 (en) * | 2011-09-21 | 2013-03-28 | The Boeing Company | Wireless refueling boom |
US20160102765A1 (en) * | 2012-12-31 | 2016-04-14 | Ge Oil & Gas Pressure Control Lp | No-bolt security latching system |
EP2574554A3 (en) * | 2011-06-03 | 2017-04-05 | Airbus Defence and Space SA | System for detecting the status of a tube for fuel transfer |
US20190071300A1 (en) * | 2017-09-01 | 2019-03-07 | Eaton Intelligent Power Limited | Fluid nozzle |
US10239631B2 (en) * | 2014-09-10 | 2019-03-26 | The Boeing Company | Aircraft receptacle |
US10279923B2 (en) * | 2015-04-27 | 2019-05-07 | Airbus Defence and Space S.A. | Contact detecting system and method for air refueling tanker equipped with air refueling boom system |
US20190264853A1 (en) * | 2018-02-26 | 2019-08-29 | Eaton Intelligent Power Limited | Low engagement force fluid coupling |
US10480675B2 (en) | 2012-12-31 | 2019-11-19 | Ge Oil & Gas Pressure Control Lp | No-bolt security latching system |
FR3081445A1 (en) * | 2018-05-24 | 2019-11-29 | Eaton Intelligent Power Limited | NOZZLE FOR FLUID |
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US2634926A (en) * | 1949-01-18 | 1953-04-14 | Flight Refueling Ltd | Apparatus for installation in aircraft for receiving fuel and other liquids in flight and control means therefor |
US3128009A (en) * | 1959-01-28 | 1964-04-07 | Geartight Unions Ltd | Closure means for pressure vessels |
US3140730A (en) * | 1961-08-16 | 1964-07-14 | Commissariat Energie Atomique | Plug for an atomic reactor channel |
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-
1981
- 1981-05-04 US US06/259,838 patent/US4438793A/en not_active Expired - Lifetime
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Cited By (60)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4535826A (en) * | 1983-08-29 | 1985-08-20 | Bell Edward D | Apparatus for rapid refueling of armored fighting vehicles |
US5004023A (en) * | 1990-03-30 | 1991-04-02 | Monticup Jr Anthony | Gasoline nozzle with emergency shut-off |
US5988332A (en) * | 1997-07-23 | 1999-11-23 | Marzocchi S.P.A. | Hydraulic shock absorber |
US20060011782A1 (en) * | 2004-07-14 | 2006-01-19 | The Boeing Company | In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components |
US7516920B2 (en) | 2004-07-14 | 2009-04-14 | The Boeing Company | In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components |
WO2006085985A1 (en) * | 2004-07-14 | 2006-08-17 | The Boeing Company | In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components |
US20080017757A1 (en) * | 2004-07-14 | 2008-01-24 | The Boeing Company | In-Flight Refueling System And Method For Facilitating Emergency Separation Of In-Flight Refueling System Components |
US7281687B2 (en) | 2004-07-14 | 2007-10-16 | The Boeing Company | In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components |
US7147186B2 (en) | 2004-11-18 | 2006-12-12 | The Boeing Company | Interoperable aerial refueling apparatus and methods |
US7793887B2 (en) | 2004-11-18 | 2010-09-14 | The Boeing Company | Interoperable aerial refueling methods |
US20060102791A1 (en) * | 2004-11-18 | 2006-05-18 | The Boeing Company | Interoperable aerial refueling apparatus and methods |
US20090039201A1 (en) * | 2004-11-18 | 2009-02-12 | The Boeing Company | Interoperable Aerial Refueling Methods |
US7431241B2 (en) | 2004-11-18 | 2008-10-07 | The Boeing Company | Interoperable aerial refueling apparatus and methods |
US20080210808A1 (en) * | 2004-11-18 | 2008-09-04 | The Boeing Company | Interoperable aerial refueling apparatus and methods |
US20060192053A1 (en) * | 2005-02-25 | 2006-08-31 | Crangle Gage B | Systems and methods for controlling flexible communication links used for aircraft refueling |
US7309047B2 (en) * | 2005-02-25 | 2007-12-18 | The Boeing Company | Systems and methods for controlling flexible communication links used for aircraft refueling |
US7469863B1 (en) | 2005-03-24 | 2008-12-30 | The Boeing Company | Systems and methods for automatically and semiautomatically controlling aircraft refueling |
US20080302916A1 (en) * | 2005-03-24 | 2008-12-11 | Speer Thomas E | Systems and methods for automatically and semiautomatically controlling aircraft refueling |
US7637458B2 (en) | 2005-06-08 | 2009-12-29 | The Boeing Company | Systems and methods for providing back-up hydraulic power for aircraft, including tanker aircraft |
US20070069071A1 (en) * | 2005-06-08 | 2007-03-29 | The Boeing Company | Systems and methods for providing back-up hydraulic power for aircraft, including tanker aircraft |
US20060278759A1 (en) * | 2005-06-09 | 2006-12-14 | The Boeing Company | System and methods for distributing loads from fluid conduits, including aircraft fuel conduits |
US20100024189A1 (en) * | 2005-06-09 | 2010-02-04 | The Boeing Company | Systems and Methods for Distributing Loads from Fluid Conduits, Including Aircraft Fuel Conduits |
US20060278763A1 (en) * | 2005-06-09 | 2006-12-14 | The Boeing Company | Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods |
US7946038B2 (en) | 2005-06-09 | 2011-05-24 | The Boeing Company | Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods |
US7922122B2 (en) | 2005-06-09 | 2011-04-12 | The Boeing Company | Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits |
US20090293256A1 (en) * | 2005-06-09 | 2009-12-03 | The Boeing Company | Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods |
US7293741B2 (en) | 2005-06-09 | 2007-11-13 | The Boeing Company | System and methods for distributing loads from fluid conduits, including aircraft fuel conduits |
US7533850B2 (en) | 2005-06-09 | 2009-05-19 | The Boeing Company | Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems |
US7581700B2 (en) | 2005-06-09 | 2009-09-01 | The Boeing Company | Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods |
US8356842B2 (en) | 2005-06-09 | 2013-01-22 | Carns James A | Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems |
US20060278760A1 (en) * | 2005-06-09 | 2006-12-14 | The Boeing Company | Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems |
US7219857B2 (en) | 2005-06-20 | 2007-05-22 | The Boeing Company | Controllable refueling drogues and associated systems and methods |
US7887010B2 (en) | 2005-06-20 | 2011-02-15 | The Boeing Company | Controllable refueling drogues and associated systems and methods |
US20060284019A1 (en) * | 2005-06-20 | 2006-12-21 | Takacs John F | Controllable refueling drogues and associated systems and methods |
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